Combustion Methods, Apparatuses and Systems

ABSTRACT

Fuel combustion and waste conversion can be achieved by passing an axial vortex stream in a combustion chamber in a first linear direction, and passing a peripheral vortex stream as a counterflow to the axial vortex stream in a direction generally opposing the first linear direction. The peripheral and axial vortex streams can be merged so that a first fuel and oxidant in the streams at least partially combust to form a product stream, the product stream moving in the first linear direction to an outlet at the second end of the combustion chamber. Vortices can be generated by tangentially introducing fluid streams into the one or more chambers. A primary chamber, a main chamber, and an afterburner chamber can be connected in series. Second fuel and pre-chambers can be used to stabilize and enhance combustion. Reagents can be introduced to refine gaseous streams including pollutants.

CROSS REFERENCE TO RELATED APPLICATIONS

This application claims the benefit of U.S. Provisional Application No.61/118,300 filed Nov. 26, 2008, which is hereby incorporated byreference in its entirety.

FIELD

This specification relates generally to apparatuses, systems and methodsfor fuel combustion. This specification also relates generally toapparatuses, systems and methods for waste conversion, pollution controland gas refinement.

BACKGROUND

The following paragraphs are not an admission that anything discussed inthem is prior art or part of the knowledge of persons skilled in theart.

U.S. Pat. No. 3,630,651 to Fay et al. discloses a dual vortex gaseousburner having a vortex tube, a separator tube, a pair of vortex chambersand an igniter. An oxidizer is injected tangentially through a jet inone of the vortex chambers forming a primary vortex between theseparator tube and the vortex tube wall, while a fuel is injectedtangentially through a jet in the other vortex chamber forming asecondary vortex between the igniter and the separator tube. An electricspark from the igniter produces ignition of the oxidizer and fuel at theboundary between the two vortices.

U.S. Pat. No. 5,055,030 to Schirmer discloses a method and apparatus forrecovering hydrocarbons in which a first toroidal vortex of fuel and acombustion supporting gas is created with its center adjacent the axisof an elongated combustor; a second toroidal vortex of combustionsupporting gas is generated between the first toroidal vortex; the fuelis burned in the presence of the combustion supporting gas to produce afuel gas at the downstream end of the combustor; water is introducedinto the flue gas adjacent the downstream end of the combustion toproduce a mixture of flue gas and water; a major portion of the water isvaporized in a vaporizor to produce a mixture of flue gas and steam; andthe mixture of flue gas and steam is injected into a hydrocarbon bearingformation.

INTRODUCTION

The following introduction is intended to introduce the reader to thisspecification. One or more inventions may reside in a combination orsub-combination of the apparatus elements or method steps describedbelow or in other parts of this document. The applicant(s) does notwaive or disclaim rights to any invention or inventions disclosed inthis specification merely by not describing such other invention orinventions in the claims.

In an aspect of this specification, a combustion method comprises:generating an axial vortex stream, and passing the axial vortex streambetween a first end and a second end of a main chamber in a first lineardirection; generating a peripheral vortex stream, and passing theperipheral vortex stream as a counterflow to the axial vortex stream ina direction generally opposing the first linear direction; and mergingthe peripheral vortex stream with the axial vortex stream to form aproduct stream, the product stream moving in the first linear directionto an outlet at the second end of the main chamber.

The axial vortex stream can include a first fuel and the peripheralvortex stream can include a first oxidant. The first fuel of the axialvortex stream and the first oxidant of the peripheral vortex stream canat least partially combust to form the product stream. The axial andperipheral vortex streams can be generated having the same rotationalpolarity. The peripheral vortex stream can be merged with the axialvortex stream proximate to the first end of the combustion chamber.

The peripheral vortex stream can be generated by tangentiallyintroducing a first stream to the combustion chamber. The first streamcan be introduced to form the peripheral vortex stream proximate to thesecond end of the combustion chamber. The first stream can include theoxidant. The first stream can include a second fuel. The first streamcan include a first pre-chamber product stream from at least one firstpre-chamber. The at least one first pre-chamber can include a source ofa second fuel, a source of the oxidant, and an ignition source. Thesecond fuel and the oxidant can have at least partially combusted in theat least one first pre-chamber to form the first pre-chamber productstream. The second fuel can have a higher heat of combustion than thefirst fuel.

The axial vortex stream can be formed upstream from an inlet at thefirst end of the main chamber, and the axial vortex stream can be passedthrough the inlet. The axial vortex stream can be generated by passing asecond stream, and tangentially introducing a third stream to combinewith the second stream. The second stream can include the first fuel andthe third stream includes the oxidant. The third stream can include asecond pre-chamber product stream from at least one second pre-chamber.The at least one second pre-chamber can include a source of a secondfuel, a source of the oxidant, and an ignition source. The second fueland the oxidant can have at least partially combusted in the at leastone second pre-chamber to form the second pre-chamber product stream.The second fuel can have a higher heat of combustion than the firstfuel.

The method can further comprise cooling the product stream to avoidrecombination of molecules. A fourth gas stream can be introduced to theproduct stream downstream from the outlet to cool the product stream.The fourth gas stream can be tangentially introduced to the productstream.

Velocities of the axial and peripheral vortex streams can be controlledto provide substantially full combustion of the first fuel and theoxidant. Compositions of the axial and peripheral vortex streams can becontrolled so as to provide a stoichiometric excess of oxidant relativeto the first and second fuels. The method can further comprisemonitoring combustion data representing at least one of temperature,fuel quantity, air quantity, and pressure, and using the data asfeedback to control the axial and peripheral vortex streams. The datacan be gathered using a microprocessor, and the microprocessor cancalculate optimum control parameters using a mathematical combustionmodel.

In another aspect of this specification, an apparatus comprises ahousing including interior sidewalls, the sidewalls defining a mainchamber, the main chamber including an inlet, an outlet, and first andsecond ends, the inlet for passing an axial vortex stream to the firstend, the axial vortex stream including a first fuel, the second endincluding an outlet for expelling a product stream, the main chamberincluding at least one first channel disposed between the first andsecond ends, the at least one first channel for introducing fluid intothe main chamber to form a peripheral vortex stream including an oxidantas a counterflow to the axial vortex stream.

The interior walls of the main chamber can be generally cylindrical andconverge in a flow direction of the axial vortex stream from the firstend to the second end. The apparatus can further comprise a mergingsurface within the main chamber for merging the peripheral and axialvortex streams. The merging surface can be located along the sidewallsof the main chamber at the first end thereof. The merging surface can befrusto-toroidal in shape. The inlet can comprise a cylindrical sleeveextending into the main chamber, the sleeve for directing flow of theaxial vortex stream into the main chamber. The sleeve can befrusto-conical in shape. The sleeve can include a plurality ofapertures.

The apparatus can further comprise a first injection zone for producinga first stream, the first injection zone in fluid communication with theat least one first channel for providing the first stream to the mainchamber, the first stream forming the peripheral vortex stream. Thefirst injection zone can be generally annular in shape and extendradially around a circumference of the main chamber. The first injectionzone can include a plurality of swirl vanes for directing rotationalfluid flow. The first injection zone can include an oxidant source forinjecting an oxidant to form at least a portion of the first stream. Theoxidant source can be tangentially aligned within the first injectionzone. The first injection zone can include a fuel source for injecting asecond fuel to form at least a portion of the first stream. The fuelsource can be tangentially aligned within the first injection zone. Thefirst injection zone can include at least one pre-chamber, the at leastone pre-chamber including a fuel source for supplying a second fuel, anoxidant source for supplying an oxidant, an igniter, and an outlet forexhausting a second pre-chamber product stream. The outlet of the atleast one pre-chamber can be tangentially aligned within the firstinjection zone.

The apparatus can further comprise a primary chamber in fluidcommunication with the inlet of the main chamber. The primary chambercan include a primary inlet for receiving a second stream, and at leastone second channel for supplying a third stream, the second and thirdstreams mixing in the primary chamber to form the axial vortex stream.The primary inlet can be connected to a source of the first fuel, thefirst fuel forming at least a portion of the second stream. Theapparatus can further comprise a second injection zone for producing thethird stream, the second injection zone in communication with the atleast one second channel for providing the third stream to the primarychamber. The second injection zone can be generally annular in shape andextend radially around a circumference of the primary chamber. Thesecond injection zone can include a plurality of swirl vanes fordirecting rotational fluid flow. The second injection zone can includean oxidant source for injecting an oxidant to form at least a portion ofthe third stream. The oxidant source can be tangentially aligned withinthe second injection zone. The second injection zone can include atleast one pre-chamber. The at least one pre-chamber can include a fuelsource for supplying a second fuel, an oxidant source for supplying anoxidant, an igniter, and a pre-chamber outlet for exhausting a secondpre-chamber product stream. The pre-chamber outlet of the at least onesecond pre-chamber can be tangentially aligned within the secondinjection zone.

The apparatus can further comprise an afterburner chamber in fluidcommunication with the outlet of the main chamber, the afterburnerchamber for receiving the product stream and cooling the product stream.The afterburner chamber can include at least one third channel forintroducing a fourth stream to the product stream, the fourth streamcomprising a coolant fluid. The apparatus can further comprise a thirdinjection zone for producing the fourth stream, the third injection zonein fluid communication with the at least one third channel for providingthe fourth stream to the afterburner chamber. The third injection zonecan be generally annular in shape and extend radially around acircumference of the afterburner chamber. The third injection zone caninclude a plurality of swirl vanes for directing rotational fluid flow.

In another aspect of this specification, a combustion system comprises:a source of a first fuel; a primary chamber connected to the source ofthe first fuel, the primary chamber receiving a second stream includingthe first fuel, the primary chamber adapted to tangentially introduce athird stream into the second stream to generate an axial vortex stream;and a main chamber connected to the primary chamber, the main chamberincluding an inlet for receiving the axial vortex stream from theprimary chamber, the main chamber adapted to tangentially introduce afirst stream to generate a peripheral vortex stream, the peripheralvortex stream moving as a counterflow to the axial vortex stream, thefirst stream including an oxidant, the first fuel in the axial vortexstream and the oxidant in the peripheral vortex stream at leastpartially combusting to form a product stream, the main chamberincluding an outlet for expelling the product stream.

In the main chamber, the first stream can be introduced adjacent to theoutlet. At least a portion of the peripheral vortex stream can flowalong a substantial length of the main chamber from the outlet to theinlet. The first stream can include the oxidant. The first stream caninclude a second fuel. The first stream can include a first pre-chamberproduct stream. The first pre-chamber product stream can include asecond fuel, the second fuel at least partially combusted in the firstpre-chamber product stream. The third stream can include the oxidant.The third stream can include a second fuel. The third stream can includea second pre-chamber product stream. The second pre-chamber productstream can include a second fuel, the second fuel at least partiallycombusted in the second pre-chamber product stream. The second fuel canhave a higher heat of combustion than the first fuel.

The system can further comprise an afterburner chamber in fluidcommunication with the outlet of the main chamber, the afterburnerchamber adapted to inject a fourth stream into the product stream, thefourth stream including a coolant fluid.

The system can further comprise a plurality of sensors for monitoringcombustion data representing at least one of temperature, fuel quantity,air quantity, and pressure. The system can further comprise amicroprocessor for collecting the data, the microprocessor adapted touse the data as feedback to control the axial and peripheral vortexstreams. The microprocessor can be adapted to calculate optimum controlparameters using a mathematical combustion model.

In another aspect of this specification, a method of gas refinementcomprises: providing an axial stream, and passing the axial stream in amain chamber in a first linear direction from a first end towards asecond end, the axial stream including at least one pollutant;generating a first peripheral vortex stream, the peripheral vortexstream including at least one reagent; and merging the first peripheralvortex stream with the axial stream to form a product stream, the atleast one pollutant and the at least one reagent at least partiallyreacting in the product stream, the product stream moving in the firstlinear direction to an outlet at the second end of the main chamber.

The at least one pollutant can be selected from the group consisting ofSO₂, NO_(x) and CO₂. The at least one first reagent can be selected fromthe group consisting of NH₃, CO(NH₂)₂, C, H₂O and CaO. The at least onepollutant is selected from the group consisting of SO₂ and NO₂, and theat least one reagent is selected from the group consisting of NH₃ andCO(NH₂)₂. The at least one pollutant comprises CO₂, and the at least onereagent is selected from the group consisting of NH₃, C, H₂O and CaO.The peripheral vortex stream further comprises at least one secondreagent selected from the group consisting of NaHCO₃, CaCO₃, CaO andCa(OH)₂.

The peripheral vortex stream can be passed as a counterflow to the axialvortex stream in a direction generally opposing the first lineardirection. The peripheral vortex stream can be merged with the axialvortex stream proximate to the first end of the main chamber. Theperipheral vortex stream can be generated by tangentially introducing afirst stream to the combustion chamber, the first stream including theat least one first reagent. The first stream can be tangentiallyintroduced proximate to a source of the at least one first reagent. Thefirst stream can comprise an oxidant. The method can further compriseintroducing a fuel to the first stream. The first peripheral vortexstream can be generated at least in part by tangentially introducing afirst pre-chamber product stream from at least one first pre-chamber.The at least one first pre-chamber can include a source of a fuel, asource of the oxidant, and an ignition source, the fuel and the oxidantat least partially combusting in the at least one first pre-chamber toform the first pre-chamber product stream. The method can furthercomprise cooling the product stream to avoid recombination of molecules.

In yet another aspect of this specification, an apparatus for gasrefinement comprises: a housing including interior sidewalls, thesidewalls defining a main chamber, the main chamber including first andsecond ends and an inlet for introducing an axial stream that passes ina first linear direction from the first end to the second end of themain chamber, the axial stream including at least one pollutant, thesecond end including an outlet for expelling a product stream; at leastone first channel disposed between the first and second ends of the mainchamber; and a first injection zone for producing a first stream, thefirst injection zone including a source of at least one first reagent,the first injection zone in fluid communication with the at least onefirst channel for providing the first stream to the main chamber to forma peripheral vortex stream, the at least one pollutant in the axialstream and the at least one reagent in the peripheral vortex stream atleast partially reacting in the product stream.

The at least one pollutant can be selected from the group consisting ofSO₂ and NO₂, and the at least one reagent can be selected from the groupconsisting of NH₃ and CO(NH₂)₂. The at least one pollutant can be CO₂,and the at least one reagent can be selected from the group consistingof NH₃, C, H₂O and CaO.

The first injection zone can be generally annular in shape and extendradially around a circumference of the main chamber. The third injectionzone can include a plurality of swirl vanes for directing rotationalfluid flow. The first injection zone can include an oxidant source forinjecting an oxidant to form at least a portion of the first stream. Theoxidant source can be tangentially aligned within the first injectionzone. The oxidant source can be proximate to the source of the at leastone first reagent. The first injection zone can include a fuel sourcefor injecting a fuel to form at least a portion of the first stream. Thefirst injection zone can include at least one pre-chamber. The at leastone pre-chamber can include a fuel source for supplying a second fuel,an oxidant source for supplying an oxidant, an igniter, and an outletfor exhausting a second pre-chamber product stream.

The apparatus can further comprise an afterburner chamber in fluidcommunication with the outlet of the main chamber, the afterburnerchamber for receiving the product stream and cooling the product stream.

DRAWINGS

The skilled person in the art will understand that the drawings,described below, are for illustration purposes only. The drawings arenot intended to limit the scope of the applicant's teachings in any way.

FIG. 1 is a schematic diagram of an apparatus according to a firstexample;

FIG. 2 is a sectional diagram of the apparatus of FIG. 1;

FIGS. 3 and 4 are sectional diagrams of the apparatus of FIG. 2 alonglines A-A and B-B, respectively;

FIGS. 5 and 6 are sectional diagrams of the apparatus of FIG. 2illustrating velocities of fluid flow;

FIGS. 7A, 7B and 7C are graphs of temperature, pressure and tangentialvelocity of fluid flow, respectively, of the apparatus of FIGS. 5 and 6along lines a-a, b-b, c-c, d-d and g-g;

FIG. 8 is a schematic diagram of an apparatus according to a secondexample;

FIG. 9 is a sectional diagram of the apparatus of FIG. 8;

FIGS. 10 and 11 are sectional diagrams of the apparatus of FIG. 9 alonglines A-A and B-B, respectively;

FIG. 12 is a schematic diagram of an apparatus according to a thirdexample;

FIG. 13 is a sectional diagram of the apparatus of FIG. 12;

FIGS. 14 and 15 are sectional diagrams of the apparatus of FIG. 13 alonglines A-A and B-B, respectively;

FIG. 16 is a schematic diagram of an apparatus according to a fourthexample;

FIG. 17 is a sectional diagram of the apparatus of FIG. 16;

FIGS. 18 and 19 are sectional diagrams of the apparatus of FIG. 17 alonglines A-A and B-B, respectively;

FIG. 20 is a schematic diagram of an apparatus according to a fifthexample;

FIG. 21 is a sectional diagram of the apparatus of FIG. 20;

FIGS. 22 and 23 are sectional diagrams of the apparatus of FIG. 21 alonglines A-A and B-B, respectively;

FIG. 24 is a schematic diagram of an apparatus according to a sixthexample;

FIG. 25 is a sectional diagram of the apparatus of FIG. 24;

FIGS. 26 and 27 are sectional diagrams of the apparatus of FIG. 25 alonglines A-A and B-B, respectively;

FIG. 28 is a schematic diagram of an apparatus according to a seventhexample;

FIG. 29 is a sectional diagram of the apparatus of FIG. 28;

FIGS. 30 and 31 are sectional diagrams of the apparatus of FIG. 29 alonglines A-A and B-B, respectively;

FIG. 32 is a schematic diagram of an apparatus according to a eighthexample;

FIG. 33 is a sectional diagram of the apparatus of FIG. 32;

FIG. 34 is a sectional diagram of the apparatus of FIG. 33 along lineA-A;

FIG. 35 is a schematic diagram of an apparatus according to a ninthexample;

FIG. 36 is a sectional diagram of the apparatus of FIG. 35;

FIG. 37 is a sectional diagram of the apparatus of FIG. 36 along lineA-A;

FIG. 38 is a schematic diagram of an apparatus according to a tenthexample;

FIG. 39 is a sectional diagram of the apparatus of FIG. 38;

FIG. 40 is a sectional diagram of the apparatus of FIG. 39 along lineA-A;

FIGS. 41, 42 and 43 are schematic diagrams;

FIG. 44 is a schematic diagram of an apparatus according to an eleventhexample;

FIG. 45 is a sectional diagram of the apparatus of FIG. 44;

FIGS. 46, 47 and 48 are sectional diagrams of the apparatus of FIG. 45along lines A-A, B-B and C-C, respectively;

FIG. 49 is a schematic diagram of an apparatus according to a twelfthexample;

FIG. 50 is a sectional diagram of the apparatus of FIG. 49;

FIGS. 51 and 52 are sectional diagrams of the apparatus of FIG. 50 alonglines A-A and B-B, respectively;

FIG. 53 is a schematic diagram of an apparatus according to a thirteenthexample;

FIG. 54 is a sectional diagram of the apparatus of FIG. 53; and

FIGS. 55 and 56 are sectional diagrams of the apparatus of FIG. 54 alonglines A-A and B-B, respectively.

DESCRIPTION OF VARIOUS EMBODIMENTS

Various apparatuses or methods will be described below to provide anexample of an embodiment of each claimed invention. No embodimentdescribed below limits any claimed invention and any claimed inventionmay cover apparatuses or methods that are not described below. Theclaimed inventions are not limited to apparatuses or methods having allof the features of any one apparatus or method described below or tofeatures common to multiple or all of the apparatuses described below.It is possible that an apparatus or method described below is not anembodiment of any claimed invention. The applicant(s), inventor(s)and/or owner(s) reserve all rights in any invention disclosed in anapparatus or method described below that is not claimed in this documentand do not abandon, disclaim or dedicate to the public any suchinvention by its disclosure in this document.

Applicant's teachings relate to the use of at least one combustionchamber in which an axial vortex stream is passed in a first lineardirection, and a peripheral vortex stream is passed as a counterflow tothe axial vortex stream in a direction generally opposing the firstlinear direction. The peripheral and axial vortex streams are merged toform a product stream, the product stream moving in the first lineardirection to an outlet of the chamber.

Applicant's teachings can be directed to a variety of application areas,including but not limited to: thermochemical processing and utilizationof solid domestic, industrial, medical and biological waste; productionof artificial fuels (for example, methanol dimethyl-ether, biodiesel,benzene); reducing the presence of airborne pollutants and/or greenhousegases from emission sources, e.g., industrial plants, coal-firedelectricity generating stations, incinerators, cars, trucks, ships,etc.; burning of gaseous waste with low thermal coefficients with stablecomposition and non-stationary parameters; burning of liquid waste withhigh and low thermal coefficients; combustion of liquid and gaseous fuelmixes (including waste); acceleration of different thermochemicalreactions; utilization in diesel generators and boilers; heatgenerations, for example, combustion systems of airplanes and ships;etc.

Applicant's teachings can be implemented as a retrofit to existingindustrial apparatuses to reduce the presence of airborne pollutantsand/or greenhouse gases from existing emission sources, and can bescalable depending on energy and waste conversion demands of aparticular application. The combustion process can becomputer-controlled, whereby feedback data can be monitored andadjustments can be made to operating parameters.

FIG. 1 shows a combustion apparatus 100 according to a first exampledescribed in this specification. The apparatus 100 includes a first orprimary combustion chamber 102. The primary combustion chamber 102 is influid connection with a second or main combustion chamber 104. The term“primary” as used herein to describe chamber 102 refers to the fact thatchamber 102 can be connected upstream from the main chamber 104, and canbe the first in a series of chambers of apparatus 100. At leastpartially combusted products exiting the main combustion chamber 104 arepassed to an afterburner chamber 106. One or more first pre-chambers 110can be provided as fluid inputs (e.g., for injection of liquid orgaseous fuels, air, oxygen, or various combinations thereof) to the maincombustion chamber 104. One or more second pre-chambers 108 can beprovided as fluid inputs to the primary combustion chamber 102.

The apparatus 100 can be used for the combustion and decomposition ofgaseous fuels or waste having relatively low heats of combustion,unstable parameters and non-standard characteristics (e.g., pressure andtemperature characteristics). For example, the apparatus 100 can beimplemented for: thermochemical processing and utilization of soliddomestic and industrial residue; processing of medical and biologicalresidue; or production of artificial fuels (for example but not limitedto methanol, dimethyl-ether, bio-diesel, benzene). In a specificexample, the apparatus 100 can be used to combust pyrolysis gasresulting from the burning of solid waste in the thermochemical reactor,the pyrolysis gas having a relatively low heat of combustion (e.g., 4-12MJ/kg) and unstable components due to different burning products andnon-stationary parameters of the gaseous quantity.

The primary combustion chamber 102 includes a fuel source 112 fordelivering a stream to the primary combustion chamber 102 comprising afirst fuel. The primary combustion chamber 102 can include an air oroxidant source 114. The main combustion chamber 104 can include a fuelsource 116 and an air or oxidant source 118. The second pre-chamber 108can include an air or oxidant source 120 and fuel source 122, and thefirst pre-chamber 110 can include an air or oxidant source 124 and afuel source 126.

Formation and burning of a fuel-air mix can take place in the primaryand main combustion chambers 102, 104. The multiple-stage combustion cantake place in sequence, providing an increase in fuel burningcompleteness. Use of the pre-chambers 108, 110 to the primary and maincombustion chambers 102, 104 can stabilize the combustion process andreduce or eliminate flame interruption during non-steady fuel supplyfrom the fuel source 112 to the primary combustion chamber 102, whichcan increase reliability and stability of the combustion process.

Referring to FIGS. 2 to 4, the main combustion chamber 104 includes agenerally cylindrical housing 128. Interior sidewalls 130 of the housing128 can be sloped according to an angle of contraction such that theradial area of the main combustion chamber 104 decreases along thelongitudinal or axial direction of the apparatus 100. The angle ofcontraction serves to maintain static pressure within the main chamber104. In some examples, the interior sidewalls 130 of the main chamber104 can converge in a flow direction according to an angle ofcontraction of about 5 to 15 degrees.

In some examples, the main chamber 104 includes an inlet 132, an outlet134, and first and second ends 136, 138. The inlet 132 can be proximateto the first end 136 and receives an axial vortex stream 140. The outlet134 can be proximate to the second end 138 and receives a product stream142, and passes the product stream to the afterburner chamber 106. Themain chamber 104 can include at least one first channel 144 disposedbetween the first and second ends 136, 138, the at least one channel 144for introducing fluid into the main chamber 104 to form a peripheralvortex stream 146 as a counterflow to the axial vortex stream 140. Theperipheral and axial vortex streams 146, 140 have the same rotationalpolarity.

In some examples, and with reference to FIG. 2 and FIG. 3 (a sectionalview along line A-A in FIG. 2), the main chamber 104 of the apparatus100 can include a first injection zone 148 for producing a first fluidstream 150 to form the peripheral vortex stream 146. The first injectionzone 148 is in fluid communication with the at least one first channel144 and delivers the first stream 150 to the main chamber 104. The firstinjection zone 148 can be generally annular in shape and extend radiallyaround a circumference of the main chamber 104. The first injection zone148 can include a plurality of swirl vanes 152 for directing rotationalfluid flow.

The first injection zone 148 can include an oxidant source 118 forinjecting an oxidant to form at least a portion of the first stream 150.The oxidant source 118 can be tangentially aligned within the firstinjection zone 148 for directing rotational fluid flow. The oxidantsource 118 can be for example but not limited to, an air ejector.

The first injection zone 148 can also include one or more fuel sources116A, 1168 for injecting a second fuel to form at least a portion of thefirst stream 150. The second fuel can be richer than the first fuel,i.e. the second fuel can have a higher heat of combustion than the firstfuel. In some examples, the fuel sources 116A, 116B can direct a liquidfuel into the first injection zone 148, the liquid fuel having arelatively high heat of combustion. The fuel sources 116A, 116B can betangentially aligned within the first injection zone 148 for directingrotational fluid flow. Fuel sources 116A, 116B need not be identical.

The first injection zone 148 can also include one or more firstpre-chambers 110A, 110B. Each of the one or more first pre-chambers110A, 110B can include respective air or oxidant sources 124A, 124B forsupplying an oxidant, fuel sources 126A, 126B for supplying a secondfuel, ignition sources or igniters 154A, 154B, and outlets 156A, 156Bfor exhausting a first pre-chamber product stream into the firstinjection zone 148. The first pre-chamber outlets 156A, 156B can also betangentially aligned within the first injection zone 148 for directingrotational fluid flow. The first pre-chambers 110A, 1106 and associatedcomponents need not be identical.

A maximum burning temperature of the product stream 142 in the mainchamber 104 can be reached due to the injection of second fuel enteringthe main chamber 104 by way of the fuel source 116 and pre-chambers 110(via the peripheral vortex stream 146). The extra supply of fuel to themain chamber 104 can provide for the near stoichiometric condition toprovide complete combustion of first fuel from the fuel source 112having relatively low heat of combustion.

Referring to FIG. 2, the main chamber 104 can further comprise a mergingsurface 158 for merging the peripheral and axial vortex streams 146,140. The merging surface 158 can be located along the interior sidewalls130 of the main chamber 104 proximate to the first end 136. The mergingsurface 158 can be frusto-toroidal in shape. The inlet 132 at the firstend 136 can include a cylindrical sleeve 160 extending into the mainchamber 104, the sleeve 160 for directing flow of the axial vortexstream 140 into the main chamber 104. The sleeve 160 can befrusto-conical in shape, and can include a plurality of apertures 162allowing for migration of fluid from the peripheral vortex stream 146into the axial vortex stream 140 near the first end 136.

With reference to FIG. 2, the primary chamber 102 can include a primaryinlet 164 for directing the gaseous fuel from the fuel source 112towards the main chamber 104. In some examples, first fuel from the fuelsource 112 and oxidant can be mixed in the primary chamber 102 and formthe axial vortex stream 140. The first fuel from the fuel source 112 andoxidant can at least partially combust in the primary chamber 102, priorto entering the main chamber 104 as the axial vortex stream 140. Inparticular, the primary chamber 102 can be in fluid communication withthe inlet 132 of the main chamber 104. The primary chamber 102 caninclude the primary inlet 164 for receiving a second stream 166, withthe first fuel from the fuel source 112 forming at least a portion ofthe second stream 166. The primary chamber 102 can further include atleast one second channel 168 for supplying a third stream 170, thesecond and third streams 166, 170 mixing in the primary chamber 102 toform the axial vortex stream 140.

In some examples, and with reference to FIGS. 2 and 4 (a sectional viewalong line B-B in FIG. 2), the primary chamber 102 of the apparatus 100can include a second injection zone 172 for producing the third stream170. The second injection zone 172 can be in fluid communication withthe at least one second channel 168 for directing the third stream 170to the primary chamber 102 to mix with the second stream 166. The secondinjection zone 172 can be generally annular in shape and extend radiallyaround a circumference of the primary chamber 102. The second injectionzone 172 can include a plurality of swirl vanes 152 for directingrotational fluid flow.

The second injection zone 172 can include an oxidant source 114 forinjecting an oxidant to form at least a portion of the third stream 170.The oxidant source 114 can be tangentially aligned within the secondinjection zone 172 for directing rotational fluid flow.

The second injection zone 172 can also include one or more secondpre-chambers 108A, 108B. Each of the one or more second pre-chambers108A, 108B can include respective fuel sources 122A, 122B for supplyinga second fuel, oxidant sources 120A, 120B for supplying an oxidant,ignition sources or igniters 154A, 154B, and second pre-chamber outlets174A, 174B for exhausting a second pre-chamber product stream into thesecond injection zone 172. The second pre-chamber outlets 174A, 174B canbe tangentially aligned within the second injection zone 172 fordirecting rotational fluid flow. The second pre-chambers 108A, 108B andassociated components need not be identical.

The use of one or more pre-chambers 108A, 108B can provide an increasein fluid velocity in the second injection zone 172 which can lead to anincrease in radial and axial static pressure gradients within theprimary combustion chamber 102. An increase in static pressure gradientscan serve to draw in first fuel from the fuel source 112, and lead to atemperature increase within the primary chamber 102, which can stabilizethe burning process of the incoming first fuel if the first fuel isunstable with non-stationary parameters.

The exit of the product stream 142 from the main chamber 104 and theentrance of the first fluid stream 150 (which forms the peripheralvortex stream 146) can be provided at roughly the same cross-sectionalposition within the main chamber 104 in a direction orthogonal to thelongitudinal axis of the main chamber 104. Consequently, the peripheralvortex stream 146 serves to cover substantially the entire length of themain chamber 104 and thus shield the interior sidewalls 130 from theaxial vortex and product streams 140, 142, which can be of relativelyhigh temperature. The sidewalls 130, therefore, can be fabricated totolerate lower temperatures. In other words, although temperatures alongthe center axis of the main chamber 104 can reach relatively highvalues, the temperature at the sidewalls 130 can remain substantiallycooler during steady state combustion as a result of the peripheralvortex stream 146. In some examples, the temperature in the axial vortexstream 140 could reach more than 2,000 degrees Celsius, whereas thetemperature at the internal walls of the main combustion chamber heatpipe does not exceed 400 to 500 degrees Celsius, resulting in improvedreliability and longer lifespan of the main chamber 104.

With continued reference to FIG. 2, the apparatus 100 can furthercomprise an afterburner chamber 106 in fluid communication with theoutlet 134 of the main chamber 104, the afterburner chamber 106 forreceiving the product stream 142 and cooling the product stream 142. Theafterburner chamber 106 can include at least one third channel 176 forintroducing a fourth stream 178 to the product stream 142. The fourthstream 172 can include a coolant fluid for reducing the temperature ofthe product stream upon exiting the main chamber 104. In some examples,the coolant fluid can be air or an inert gas. A third injection zone(not shown) can be provided for producing the fourth stream 178, thethird injection zone being in fluid communication with the at least onethird channel 176 for directing the fourth stream 178 to the afterburnerchamber 106. Similar to the injection zones 148, 172, the thirdinjection zone can be generally annular in shape and extend radiallyaround a circumference of the afterburner chamber 106.

In the afterburner chamber 106, the product stream can be cooled toprevent or reduce recombination of molecules. In particular, theafterburner chamber 106 can provide for finalizing of the fuel burningand accordingly decreasing of emissions by mixing, dilution and coolingof the burned products. Also, the use of the kinetic energy of theproduct stream 142 from the main chamber 104 can require less relianceon external air or oxidant sources. The afterburner chamber 106 canexpel the cooled product stream 142 through the afterburner outlet 180.

FIG. 5 illustrates the distribution of tangential component, w_(φ), offluid flow velocity within the main chamber 104 at variouscross-sections. FIG. 6 illustrates the distribution of axial component,w_(z), of fluid flow velocity within the main chamber 104 at variouscross-sections. The w_(φ) and w_(z) profiles illustrate the mixing ofthe axial and peripheral vortex streams 140, 146 within the main chamber104.

With reference to cross-section a-a in FIGS. 5 and 6, the second stream166 including first fuel from the first fuel source 112 (e.g.,pyrolysis, synthetic, bio gases, etc.) can be supplied to the primarychamber 102 at atmospheric pressure or can be pressurized. The apparatus100 can achieve refinement of components of the first fuel, which cancontain partially burned hydrocarbons CH_(x), carbon monoxide CO,sulphur dioxide SO₂ and/or nitrogen oxide NO_(x). Between cross-sectionsa-a and b-b in FIGS. 5 and 6, the second stream 166 can be acceleratedas the radial cross-sectional area of the primary chamber decreasestowards the primary inlet 164, resulting in a pressure change betweenthe cross-sections a-a and b-b. The pressure can be modeled using thefollowing equation:

$\begin{matrix}{{P^{*} = {P + {\rho \frac{\omega^{2}}{2}(1)}}},} & \left( {{Eq}.\mspace{14mu} 1} \right)\end{matrix}$

where: P* is the complete pressure of the gas stream, [Pa]; P is thestatistical pressure of the gas stream, [Pa];

$\rho \frac{\omega^{2}}{2}$

is the dynamic pressure of the gas stream or speed pressure, [Pa],[kg/m³·m²/s²]; ρ is the density of the gas, [kg/m³]; w=√{square rootover (w_(z) ²+w_(φ) ²)} is the total stream speed, [m/s]; w_(z) is theaxial component of the speed; and w_(φ) is the tangential component ofthe speed.

Alternatively, it is possible to use the following equation to model thepressure:

$\begin{matrix}{{P^{*} = {P\left( {1 + {\frac{k - 1}{2} \times M^{2}}} \right)}^{\frac{k}{k - 1}}},} & \left( {{Eq}.\mspace{14mu} 2} \right)\end{matrix}$

where: k is the adiabat constant of the gas

$\left( {{k = \frac{C_{p}}{C_{v}}},} \right.$

where C_(p) is the isobar thermal capacity of the gas [kJ/kg·K] andC_(v) is the isochronous thermal capacity of the gas, [KJ/kg·K]); M isthe Mach's number in the stream; w is the total stream speed; a is theacoustic speed of the stream; R is the constant of the supplied gas(depends on the gas components); and T is the gas temperature.

FIGS. 7A, 7B and 7C show qualitative flow structure changes in thecombustion chamber as a function of location, and require reference tosectional lines a-a, b-b, c-c, d-d and g-g in FIGS. 5 and 6. FIG. 7Ashows change of the average full temperature in the axial (I) andperipheral flows (II) at specific locations. FIG. 7B shows change of thefull pressure P in the peripheral (I) and axial flows (II); and averagevalues of static pressure P in the peripheral (III) and axial pressureof the axial flow (IV). FIG. 7C shows change of maximal tangentialvelocity w_(φ), average tangential velocity w_(z) in the peripheral flow(curves I and II, respectively), and change of axial velocity w_(z) onthe central axis of the axial flow (III).

During the movement of the second stream 166 along a-a to b-b, atemperature drop can be possible. Pressure change between a-a to b-bwithout a pressurized supply from fuel source 112 can be provided by theincoming pressure of the third stream 170 from the first injection zone148.

In the cross-section b-b, relatively high centrifugal forces can beacting in accordance with the following equation:

$\begin{matrix}{{F_{y} = \frac{m\; W_{\phi}^{2}}{z}},} & \left( {{Eq}.\mspace{14mu} 3} \right)\end{matrix}$

where: m is the mass of the gas [kg]; W_(φ) is the tangential componentof the speed in this cross-section [m/s]; and z is the radius where thegas element is located [m].

A high gradient of static pressure can be formed by the centrifugalforces in cross-section b-b. Therefore, the static pressure of the fluiddecreases along the radius of the cross-section, and it reaches minimalvalue on the center axis (see FIG. 5). The reduction of static pressureleads to the axial gradient of static pressure formation. Therefore, theaxial speed of the fluid flow, which moves away from the cross-sectiona-a, is increasing. The speed reaches its maximum in the cross-sectionb-b. The growth of axial fluid component leads to the growth of dynamicpressure in the stream at constant pressure, which is inflowing from thesource 112 into the cross-section a-a, in accordance with the Equation(1).

Between b-b and c-c in the primary chamber 102, the fuel air mixture isformed, comprising first fuel from source 112, oxidant from source 114,pre-chamber product stream from pre-chamber 108, and a portion of theperipheral vortex stream 146 that passes through the apertures 162 tocombine with the axial vortex stream 140.

The burning process of the fuels between b-b and c-c can cause thetemperature to increase rapidly (see FIG. 7A). The temperature increasecauses a corresponding increase in the volume consumption of thereactants. Decline of the axial velocity between b-b and c-c (see FIG.7B) leads to a static pressure increase. FIG. 7C shows the distributionof tangential w_(φ) and axial w_(z) speeds in the cross-sections b-b andc-c, with the tangential speed w_(φ) of the peripheral vortex streambeing significantly lower than the tangential speed of the axial vortexstream. Additionally, the reduction of the pressure due to fluidentering from the peripheral vortex stream flow 146 into the axialvortex stream 140 through the apertures 162 contributes to the reductionof the axial speed of the axial vortex stream 140. This reduction isoffset by the increase in the consumption of reactants between b-b andc-c.

At cross-section d-d, the first stream 150 enters the first channel 144and forms the peripheral vortex flow 146 with axial component speedw_(z). The distribution of tangential and axial components of the speedin the cross-section d-d is shown in FIGS. 5 and 6. The maximum value ofthe tangential component of the speed is approximately located at theborderline between the peripheral vortex stream 146 and the productstream 142.

Between c-c and d-d, the peripheral vortex stream 146 is losing itstangential speed adjacent to the product stream 142. In addition, alongwith a reduction of the axial speed of the peripheral flow, masstransfer from the peripheral vortex stream 146 to the product stream 140(moving in generally opposite linear direction) intensifies due to theformation of anisotropic turbulence between the streams.

The temperature changes of the gas in axial (I) and peripheral (II)streams are shown in FIG. 7A. The temperature of the burning productscontinues to grow rapidly starting from cross-section c-c. It reachesits maximum in the burning zone near the first end 136 of the mainchamber 104, and then it decreases due to the cooler fluid supply fromthe peripheral vortex stream, preventing or reducing recombination ofmolecules.

FIG. 7B shows the change of the complete pressure P* of the peripheral(I) and axial flows (II). The reduction of the complete pressure P* inthe peripheral flow, while it is moving towards the cross-section b-b,can be explained by hydraulic losses. The reduction of the completepressure P* of the axial flow, while it is moving from the cross-sectionc-c to the cross-section d-d, can be explained by transfer of thepressure to heat and hydraulic losses. In addition, pressure reductionin the peripheral and axial streams can also be attributed to energylosses in generating turbulence between counterflows.

FIGS. 8 to 11 show a combustion apparatus 200 according to a secondexample described in this specification. The apparatus 200 is similar tothe apparatus 100, with like features identified by like referencenumbers. In particular, the first injection zone 248 does not include apre-chamber.

The apparatus 200 can be used for the combustion and decomposition ofgaseous fuels or waste having relatively low heats of combustion, stableparameters and non-standard pressure and temperature characteristics. Ina particular example, the apparatus 200 could be used for heatproduction systems (e.g., coal-fired electricity plants) usingafter-burning of gaseous substances for production of specificsubstances and their regeneration. In some examples, the apparatus 200can be utilized for burning pyrolysis gas produced during the processingof industrial waste, e.g., polishing discs, wood waste, etc. Thepyrolysis gas obtained in these processes can have relatively low heatsof combustion, unstable composition, significant amount of hydrocarbons,and non-stationary consumption parameters. In examples involvingcombustion of pyrolysis gas from a thermal-chemical reactor, negativepressure of the second stream 266 from the fuel source 212 can bedesirable to prevent or reduce leakage of pyrolysis gas to theatmosphere. In such examples, an ejector can be placed at the inlet tothe primary chamber 202 to pressurize the second stream 266, e.g., −5 to0 mm of water column.

Stable composition of the gaseous fuels permits the use of the mainchamber 204 without a pre-chamber. Similar to the apparatus 100,stabilization of the burning process can take place due to the use of atleast one pre-chamber 208 connected to the second injection zone 272 ofthe primary chamber 202.

In contrast with the apparatus 100, thermal stress within the firstinjection zone 248 and on the sidewalls 230 of the main chamber 204 canbe reduced due to the absence of burning products streaming into and outof the first injection zone 248. Furthermore, the system of air and fuelsupply to the first injection zone 248 of the main chamber 202 can besimplified.

FIGS. 12 to 15 show a combustion apparatus 300 according to a thirdexample described in this specification. The apparatus 300 is similar tothe apparatuses 100 and 200, with like features identified by likereference numbers. In particular, the second injection zone 372 does notinclude a pre-chamber.

The apparatus 300 can be used for the combustion and decomposition ofgaseous fuels or waste having relatively low thermal capacity, stableparameters, stable pressure and temperature characteristics, but withpressurized supply of the fuel to the primary chamber 302. In someexamples, the apparatus 300 can be used for thermo-chemical wasteprocessing installations where pressure below atmosphere is notrequired. In other examples, the apparatus 300 can be used forafterburning of burned products of harmful emissions (e.g., caremissions).

The flow formation within the primary chamber 302 is due to the use ofthe oxidant source 314 introduced tangentially within the secondinjection zone 372. In some examples, the oxidant source 314 can includean air ejector, with the air from the ejector mixing with the first fuelto form the axial vortex stream 140. Similar to the apparatus 100,stabilization of the burning process can take place due to the use of atleast one pre-chamber 310 connected to the first injection zone 348 ofthe main chamber 304.

In contrast with the apparatus 100, thermal stress within the secondinjection zone 372 and within the primary chamber 302 can be reduced dueto the absence of a burning products streaming into and out of thesecond injection zone 372. Furthermore, the radial gradient of staticpressure at the entrance of the primary chamber 302 can be reduced.Moreover, construction of the primary chamber 302 can be simplified dueto the absence of a pre-chamber.

FIGS. 16 to 19 show a combustion apparatus 400 according to a fourthexample described in this specification. The apparatus 400 is similar tothe apparatuses 100, 200 and 300, with like features identified by likereference numbers. In particular, the first injection zone 448 does notinclude a pre-chamber, and the second injection zone 472 does notinclude an oxidant source.

The apparatus 400 can be used for the combustion and decomposition ofliquid fuels having both low and high heats of combustion. Inparticular, the apparatus 400 can be used to achieve simultaneousburning of liquid waste with high and low heats of combustion, e.g.,simultaneous burning of sewage and oil refinery waste (benzene, acetone,etc). The apparatus 400 can also be used in industrial constructiondevices with sewage and liquids having high heats of combustion, such aspaint industry with sewage and different chemicals, alcohol productionindustry with sewage and alcohol waste, liquids used to wash heatingtanks, etc.

For the burning of liquid fuels with low and high heats of combustionsimultaneously, the fuel with higher heat of combustion can be providedusing one or more fuel sources 416, connected to the first injectionzone 448. The fuel with lower heat of combustion can be provided throughthe fuel source 422 of the one or more pre-chambers 408 connected to thesecond injection zone 472. Alternatively, the fuel with higher heat ofcombustion can be provided through the fuel source 422 of the one ormore pre-chambers 408 connected to the second injection zone 472.Oxidant or air from the oxidant source 418 and fuel from the fuel source416 can mix in the first injection zone 448 and enhance the quality ofburning downstream in the main chamber 404. Similar to the apparatuses100 and 200, stabilization of the burning process can take place due tothe use of at least one pre-chamber 408 connected to the secondinjection zone 472 of the primary chamber 402.

In contrast with the apparatus 100, thermal stress within the firstinjection zone 448 and on the sidewalls 430 of the main chamber 404 canbe reduced due to the absence of a burning products from a pre-chamber,and thermal stress within the second injection zone 472 and within theprimary chamber 402 can be reduced due to the fact that the burningprocess there takes place with reduced oxidant or air. The constructionof the primary and main chambers 402, 404 is also simplified due to theabsence of a pre-chambers and oxidant sources, respectively.

FIGS. 20 to 23 show a combustion apparatus 500 according to a fifthexample described in this specification. The apparatus 500 is similar tothe apparatuses 100, 200, 300 and 400, with like features identified bylike reference numbers. In particular, the first injection zone 548 doesnot include an oxidant source (separate from the pre-chambers 510).Accordingly, all oxidant or air present in the peripheral vortex stream546 originates from the oxidant source 524 of the one or morepre-chambers 510.

The apparatus 500 can be used for the combustion and decomposition ofgaseous fuels or waste having relatively low heats of combustion,unstable parameters and non-standard characteristics simultaneously withgaseous wastes that result from the burning of liquid waste having highheats of combustion. In some examples, the apparatus 500 can be used forafter-burning of gaseous emissions containing unburned hydrocarbons forthe purpose of controlling emissions.

The at least one pre-chamber 510 can be operated such that the air oroxidant source 524 provides an excess of air for the burning of secondfuel from the fuel source 526, and subsequently the fuel from fuelsource 516. Fuels injected via sources 526 or 516 can be the same ordifferent. Similar to the apparatuses 100 and 300, stabilization of theburning process can take place due to the use of at least onepre-chamber 510 connected to the first injection zone 548 of the mainchamber 504.

In contrast with the apparatus 100, the construction of the main chamber504 can be simplified as a result of the absence of a direct oxidantsource and necessary connections. Furthermore, velocity of theperipheral vortex stream 546 in the main chamber 504 can be increased,and accordingly the level of radial and axial gradients of staticpressure can be increased, leading to an increase in turbulence andintensification of combustion.

FIGS. 24 to 27 show a combustion apparatus 600 according to a sixthexample described in this specification. The apparatus 600 is similar tothe apparatuses 100, 200, 300, 400 and 500, with like featuresidentified by like reference numbers. In particular, the secondinjection zone 672 does not include an oxidant source (separate from thepre-chambers 608). Accordingly, all oxidant or air present in the axialvortex stream 640 originates from the oxidant source 620 of the one ormore pre-chambers 608.

The apparatus 600 can be used for the combustion of gaseous waste withlow heats of combustion, with unstable compositions, and non-stationaryparameters, jointly with gaseous waste that results from the burning ofliquid waste. Additional fuel (i.e. the second fuel) is provided throughthe first injection zone 648 to increase the temperature in the mainchamber 604 to a maximum, thus enabling decomposition and burning ofhydrocarbons, resulting in relatively low emissions in the productstream 642.

In contrast with apparatus 100, the quality of the mix in the primarychamber 602 can be increased due to the increase of the temperature andair consumption which enters with the burning product stream from the atleast one pre-chamber 608. Consumption of the fuel from the pre-chamber608 of the primary chamber 602 can be increased. Accordingly, radial andaxial gradients of static pressure can be increased at the inlet 664 ofthe primary chamber 602, which can lead to improvement of the injectionproperties of the second injection zone 672 and pressure decrease ofgaseous and liquid fuel mix entering the primary chamber 602. Absence ofan oxidant source in the second injection zone 672 simplifiesconstruction of the primary chamber 602.

FIGS. 28 to 31 show a combustion apparatus 700 according to a seventhexample described in this specification. The apparatus 700 is similar tothe apparatuses 100, 200, 300, 400, 500 and 600, with like featuresidentified by like reference numbers. In particular, the first injectionzone 748 does not include an oxidant source (separate from thepre-chambers 710), and the second injection zone 772 does not include anoxidant source (separate from the pre-chambers 708). Accordingly, alloxidant or air present in the axial and peripheral vortex stream 740,746 originates from the oxidant sources 720, 724 of the pre-chambers708, 710.

The apparatus 700 can be used for the combustion of gaseous fuel withlow heats of combustion, non-stable composition and non-stationaryparameters, jointly with gaseous waste resulting from the burning ofliquid waste with low heats of combustion. The apparatus 700 is similarto the apparatus 600, with the difference that the burning process inthe main chamber 704 can be more intense than that of the main chamber604. The apparatus 700 can be useful for mobile systems.

All oxidant or air for the working process in the primary and mainchambers 702, 704 enters from their respective pre-chambers 708, 710.The maximum temperature in the burning zone of the main chamber 704 canbe achieved due to the burning of fuel having a relatively high heat ofcombustion, which enters the main chamber 704 via source 716. Absence ofan oxidant source in the first or second injection zones 748, 772simplifies construction of the primary and main chambers 702, 704.

FIGS. 32 to 34 show a combustion apparatus 800 according to an eighthexample described in this specification. The apparatus 800 is similar tothe apparatuses 100, 200, 300, 400, 500, 600 and 700, with like featuresidentified by like reference numbers. In particular, the apparatus 800does not include a primary chamber. All reactants entering the mainchamber 804 are injected via the first injection zone 848 through the atleast one first channel 844, forming the peripheral vortex stream 846.The peripheral vortex stream 846 travels within the main chamber 804towards the first end 836 thereof. A generally spherical end surface 882causes the peripheral stream to merge inwardly to form an axial vortexstream 840. The axial vortex stream 840 acts as a counterflow to theperipheral vortex stream 846, moving in generally opposite lineardirection. The peripheral and axial vortex streams 846, 840 can have thesame rotational polarity.

The apparatus 800 can be used for the combustion and decomposition ofliquid fuels having a low and high thermal capacity, with stableparameters. The first liquid fuel is provided to the main chamber 804via fuel source 816. In some examples, the first fuel can be a wateremulsion fuel. A second fuel, which can be gaseous fuel having a higherheat of combustion than the first fuel, can be provided to the mainchamber via fuel source 826. Oxidant or air is provided to the mainchamber via oxidant sources 818, 824. Stabilization of the combustioncan be realized by the at least one pre-chamber 810, that serves toignite a fuel-air mixture.

FIGS. 35 to 37 show a combustion apparatus 900 according to a ninthexample described in this specification. The apparatus 900 is similar tothe apparatuses 100, 200, 300, 400, 500, 600, 700 and 800, with likefeatures identified by like reference numbers. In particular, similar tothe apparatus 800, the apparatus 900 does not include a primary chamber.

The apparatus 900 can be used for the combustion and decomposition ofliquid and gas fuels having high heat of combustion with stationarycharacteristics and stable parameters. The apparatus 900 is similar toapparatus 800, except that the liquid or gaseous fuels burned haverelatively high heats of combustion. The apparatus 900 can be utilizedfor combusting gas, liquid fuel, or a combination of two or three phasefuels.

In apparatus 900, the at least one pre-chamber 910 works as an igniter.The formation of the air-fuel mix begins in the first injection zone 948and forms the peripheral vortex stream 946, which in turn forms theaxial vortex stream 940.

FIGS. 38 to 40 show a combustion apparatus 1000 according to a tenthexample described in this specification. The apparatus 1000 is similarto the apparatuses 100, 200, 300, 400, 500, 600, 700, 800 and 900, withlike features identified by like reference numbers. In particular,similar to the apparatuses 800 and 900, the apparatus 1000 does notinclude a primary chamber. In contrast with apparatuses 800 and 900, thefirst injection zone 1048 does not include an oxidant source (separatefrom the pre-chambers 1010). The formation of the air-fuel mixture canbe intensified due to the fact that it takes place in the product streamof the at least one pre-chamber 1010. The burning process in theapparatus 1000 can be more intense, relative to apparatuses 800 and 900,because of increasing speed of the air-fuel mixture, high centrifugalforces, high anisotropic turbulence and acoustic vibration.

The apparatus 1000 can be used for the combustion and decomposition ofliquid fuels, gaseous fuels, solid fuels, dust-like fuels, and two andthree phase fuels. The apparatus 1000 can be particularly useful forsystems where multi-phase fuels are used, e.g., burning of solid ordust-like fuels such as wood dust, coal dust, sometimes mixed withliquid fuels (liquid hydrocarbons) or gaseous fuels (natural gas, blackoil, bio-gas, synthetic gas), etc.

FIG. 41 illustrates an example of a fuel combustion system 2000including apparatus 100, and further including various power and controlcomponents. Although the system 2000 is shown in association with theapparatus 100, it should be appreciated that other systems are possibleand contemplated in association with the apparatuses 200, 300, 400, 500,600, 700, 800, 900, 1000.

With reference to FIG. 41 (and with continued reference to FIGS. 1 to4), air from a compressor 2002 passes through valve 2004 and enters oneor more pre-chambers 110, and through valve 2006 is directed to the mainchamber 104 via 118 (i.e. to the first injection zone 148). The amountof air can be controlled by a variable frequency drive 2008, which inturn controls the compressor 2002. Airflow to the main chamber 104 isthereby controlled with valves 2004, 2006. Similarly, air fromcompressor 2010 flows through valve 2012 to one or more pre-chambers108, and through valve 2014 to the primary combustion chamber 102 via114 (i.e. to the second injection zone 172). The amount of air iscontrolled by variable frequency drive 2016, which in turn controls thecompressor 2010. Airflow to the primary chamber 102 is therebycontrolled with valves 2012, 2014. Second fuel from pump 2018 throughvalves 2020, 2022, 2024 flows to pre-chambers 108, 110 via 122, 124,respectively and directly to the main chamber 104 via 116. The flow ofsecond fuel is thereby controlled by valves 2020, 2022, 2024, and byvariable frequency drive 2026. The valves 2020, 2022, 2024 can be, forexample but not limited to, adjustable needle valves with AC/DC drives.The valves 2004, 2006, 2012, 2014 can be, for example but not limitedto, pneumatic valves with AC/DC actuators. In the pre-chambers 108, 110,a mixture of air and second fuel is formed. The mixture of air andsecond fuel can be at least partially combusted in the pre-chambers 108,110 prior to being injected into the first and second injection zones inthe form of first and second pre-chamber product streams. The first andsecond pre-chamber product streams can accelerate the air that isintroduced into the first and second injection zones 148, 172 bycompressors 2002, 2010. The combination of combustion product streamsand compressed air then feed into first and second injection zones 148,172 of the main and primary chambers 104, 102, thereby generating theaxial and peripheral vortex streams 140, 146. The second fuel thatenters the main chamber 104 and driven by the fuel pump 2018 throughvalve 2022 mixes with the air, and can at least partially combust. Thefirst fuel enters the primary chamber 102 from source 112. The productstream 142 formed in the main chamber 104 enters the afterburner chamber106, which is located downstream from the main chamber 104. In theafterburner chamber 106, the product stream is cooled to prevent orreduce recombination of molecules before exiting outlet 180.

The inventors have developed a mathematical model to establish andcontrol system parameters to optimize combustion performance. Control ofprimary parameters using a computer or microprocessor means can providefor system performance optimization. Optimization can serve to reducethe energy supply to the system, improve emission reduction and increaseburning efficacy of a broad range of fuels. The mathematical model canpermit the ability to perform analytical modeling of the combustionchamber system for different configurations and applications to obtainthe values of combustion parameters and configurations.

In accordance with the mathematical model, the following parametricequation consists of the product of several dimensionless complexparameters:

A _(ij) ×F _(ij) ×B _(ij) ×C _(ij) ×G _(ji)=1  (Eq. 4)

A_(ij), F_(ij) B_(ij), C_(ij), and G_(ji) are the integral parameterswhich define the working characteristics and geometric sizes ofcomponents of a given combustion system, where: A_(ij) is a thermalparameter and depends on the air excess coefficient during fuelcombustion, temperatures of the fuel combustion, air and fueltemperature at the entrance to the primary and main chambers andpre-chambers, and type of first and second fuels and their chemicalcomposition; F_(ij) is a geometry parameter and depends on the geometryof each component of the apparatus; B_(ij) is a first hydrodynamicparameter and depends on the relative speed of incoming and outgoingreactants and product in each component of the apparatus; C_(ij) is asecond hydrodynamic parameter and depends on the static pressure ofreactants products in each of the components of the apparatus; andG_(ij) is an emission parameter and depends on air consumption in themain and primary combustion chambers. The indices i and j correspondwith the entrance and exit, respectively, to each chamber of theapparatus.

The parameter A_(ij) determines the working regime, based on thefollowing correlations: coefficients of air excess; fuel composition;temperature of the reactants and products, which are supplied into theprimary and main combustion chamber and pre-chambers. The air excesscoefficient should be α₀=α_(p)=0 for the air, which is supplied throughthe injection zones of the primary and main combustion chambers. Thus:

A _(ij) =A _(ij)(α_(i),α_(j) ,L _(oi) ,L _(oj) ,H _(ui) ,H _(uj) ,T _(i)^(B) ,T _(j) ^(B) ,T _(i) ^(T) ,T _(i) ^(T)),  (Eq. 5)

where: α_(i), α_(j) are coefficients of the air excess; L_(oi), L_(oj)(kg air/kg fuel) are coefficients which take into consideration thequantity of the air required for the burning of 1 kg of the fuel;H_(ui), H_(uj) (kJ/kg) are combustion heat coefficients of 1 kg of thefuel; T_(i) ^(B), T_(j) ^(B) (K) are air temperatures at the entrance;and T_(i) ^(T), T_(j) ^(T)(K) are fuel temperatures at the entrance.

The geometric parameter F_(ij) determines the influence of the geometricsizes of the main components of the primary and main combustion chamberson the flow path of a given combustion system. Therefore, the mainelements of the flow path include size and shape of the injection zonesof the primary and main chambers, pre-chamber outlets to the injectionzones and location of the pre-chambers, inlets and outlets of theprimary and main chambers, etc.

The parameter B_(ij) determines the influence of the non-dimensionalspeed of streams within the chambers, where:

B _(ij) =B _(ij)(M _(i) ,M _(j)),  (Eq. 6)

where M_(i) and M_(j) are the Mach's numbers of the corresponding flowcross-section.

The parameter C_(ij) determines the influence of static pressures in theperipheral vortex formation, where:

C _(ij) =C _(ij)(P _(i) ,P _(i) and other),  (Eq. 7)

where P_(i), P_(j) are static pressures in the correspondingcross-section of the flow.

The parameter G_(ji) determines the correlation of the consumption inthe related cross-section of the flow, where:

G _(ji) =G _(ji)(G _(j) ,G _(i)),  (Eq. 8)

where G_(j) and G_(i) reflect air consumption.

Referring to FIG. 42, an example of a fuel combustion system 3000 isshown schematically including main chamber 104 of apparatus 100 (seeFIGS. 1 and 2), and further including a feedback means based on themathematical model described above. Second fuel can be supplied by thefuel tanks/pumps 3026, 3028, 3030 and can be controlled (velocity andtemperature) using valves 3002, 3004, 3006 (or more). An air compressor3018 and a water supply 3020 can respectively supply air and water tothe combustion chamber using valves 3008, 3010. The mixers/selectors3012, 3014 are controllable and connect the valves 3002, 3004, 3006,3008, 3010 with the apparatus 100. The mixers/selector 3012 can provideinitial conditions to the main chamber 104 via valves 3002, 3004, 3006upon startup. A heater 3032 can be operably connected to themixers/selectors 3012, 3014 to increase temperature of fluids beforedelivery to the main chamber 104.

The microprocessor control unit 3016 can be a small computer on a singleintegrated circuit consisting of a relatively simple CPU combined withsupport functions such as a crystal oscillator, timers, watchdog, serialand analog connections, etc. Program memory in the form of flash orOTPROM can also be included, typically along with limited read/writememory. In some examples, the microprocessor control unit 3016 caninclude a PIC16, PIC18 or dsPIC30 device. A computer 3022 can beconnected to the microprocessor control unit 3016, for example, viaRS-232 through a DB9 serial connector. An interface 3024 to themicroprocessor control unit 3016 can include a keypad and a display.

Using feedback means, the temperature in the combustion zone of the mainchamber 104 can be measured and supported at its maximum value, toprovide decomposition and burning of all organic fuel components bycontrolling the coefficient of the air excess and fuel consumption viathe main combustion fuel source. For this purpose, in some examples, tosupport the maximum temperature the coefficient of the air excess can beselected between 1.01 and 1.05. At the outlet 134 of the chamber 104, agas analyzer can provide measurement of residual contaminant in theproduct stream and this information can be fed back to a microprocessorcontrol unit 3016. The microprocessor control unit 3016 can provideinitial settings of one or more primary parameters. With the feedbackfrom the gas analyzer, general optimization of primary parameters can beachieved.

Referring back to FIGS. 1 to 4, it can be preferable to set aside afixed time for the fuels and oxidants to be in the primary and mainchambers 102, 104 at maximum temperature to provide for full combustionand decomposition of all organic fuel components, along with theprevention and/or delay of synthesis of harmful molecules, e.g., NO_(x).Residence time can be adjusted by control of the average velocity of theaxial vortex stream 140 and the total incoming air pressure to the main,primary and pre-chambers 104, 102, 108, 110. Emission parameters can bemeasured at the exit of the afterburner chamber 106 and can be optimizedaccording to monitoring and adjustment of: coefficient of air excess,fuel consumption in the primary and main chambers and pre-chambers, andtotal air pressure in the primary and main chambers and pre-chambers.Additional feedback for the optimization of combustion can beaccomplished by measuring various parameters including: temperature ofthe inlet and outlet of the primary and main chambers 102, 104 (e.g.,using an optical meter, pyrometer or other optical spectroscopy means);fluid velocities at various points (e.g., using a tachometer); fuelemission of the one or more pre-chambers 108, 110 and first and secondfuel sources 112, 116, 122, 126; controlling quantity of air in theprimary and main chambers 102, 104; pressure of the stream comprisingfirst fuel provided to the primary chamber 102; etc. The data can beused in addition to the main feedback to obtain greater control on thecombustion process.

FIG. 43 provides further details of an example implementation of thesystem 3000 shown in FIG. 42. The interface 3024 can include a keypad3034 and a display 3036. The keypad 3034 can connect to themicroprocessor control unit 3016, for example, by an 8-pin connection.The display 3036 can connect to the microprocessor control unit 3016,for example, via SPC or I2C bus connection. In some examples, thedisplay 3036 can be an LCD display. Analog signals from the sensors 3038in the chamber and sensors 3040 in or near the outlet of the chamber canbe provided to the microprocessor control unit 3016 by means ofanalog-to-digital conversion. The analog-to-digital conversion can alsoallow for two-way communication so that the microprocessor control unit3016 is capable of sending data to the sensors 3038 and/or the sensors3040. The microprocessor control unit 3016 can be connected to theheater 3032 and the valves 3002, 3004, 3006, 3008, 3010 using forexample, SPC or I2C bus connections, and can include a means fordigital-to-analog conversion. Actuators of the heater 3032 and thevalves 3002, 3004, 3006, 3008, 3010 can operate with relatively high ACor DC voltage, so proper drivers or signal transmitters isolated fromany electrical connection, for example, a photocoupler, can be provided.The microprocessor control unit 3016 can be further connected to abeeper 3042 by chip select connection. The beeper 3042 can be apiezoelectric device and serve as an alarm or indicator to providefeedback to an operator. The system 3000 can be implemented to operateand control the apparatus 100 in substantially real-time. Themicroprocessor control unit 3016 can work generally independently tocalculate various parameters from the sensors 3038, 3040 and to controlthe actuators of the heater 3032 and the valves 3002, 3004, 3006, 3008,3010. In addition, some parameters can be modified through RS-232protocol, which can also be used to accumulate data for improvement ofthe system's performance and statistics.

Using a prototype model of the apparatus 100, the inventors ran averification test to confirm the results of the mathematical modeldescribed above. The test results are provided below in Table 1. Therelative low error values indicate reasonable validation of the model.

TABLE 1 Version dc = 0.227 dc = 0.273 1 2 3 4 1 2 Absolute air KPa 241235 248 252 181 181 pressure at main chamber inlet Air temp at K 300 300300 300 300 300 main chamber inlet Air temp at K 340 360 380 400 320 360first injection zone Main g/s 132 132 132 132 132 132 chamber airconsumption Main g/s 7.4 8.0 8.4 9.0 7.2 8.0 chamber fuel consumptionExcess air — 1.209 1.120 1.065 0.994 1.240 1.120 coefficient Average airK 1500 1600 1840 1860 1480 1600 temp at main chamber outlet Mach number— 0.680 0.758 0.739 0.746 0.902 0.985 in first injection zone Speed infirst m/s 243 263 264 273 304 342 injection zone Mach number — 0.8110.827 0.877 0.854 0.789 0.786 of stream at main chamber outlet Averagegas m/s 571 602 685 670 552 572 consumption at main chamber outletExperimental parametric results A_(oc) × F_(oc) × B_(oc) × C_(oc) ×G_(oc) = 1 ± Δoc A_(oc) — 2.218 2.236 2.340 2.156 2.268 2.236 F_(oc) —0.441 0.305 B_(oc) — 0.931 1.026 0.936 0.974 1.195 1.460 C_(oc) — 1.0791.121 1.099 1.127 1.196 1.143 G_(oc) — 1.056 1.060 1.064 1.068 1.0541.061 Δoc — 0.037 0.202 0.129 0.115 0.043 0.207 δoc % 3.7 20.2 12.9 11.54.3 20.7 Version dc = 0.273 dc = 0.527 3 4 5 1 2 3 Absolute air KPa 201201 201 161 188 166 pressure at main chamber inlet Air temp at K 300 300300 300 300 300 main chamber inlet Air temp at K 400 400 330 320 400 325first injection zone Main g/s 132 132 132 132 132 132 chamber airconsumption Main g/s 8.4 9.0 9.8 7.2 9.0 9.8 chamber fuel consumptionExcess air — 1.070 0.992 0.913 1.243 0.992 0.909 coefficient Average airK 1830 1860 1460 1480 1860 1420 temp at main chamber outlet Mach number— 0.934 0.934 0.823 0.973 0.990 1.000 in first injection zone Speed infirst m/s 342 342 274 328 366 330 injection zone Mach number — 0.8320.795 0.860 0.300 0.334 0.297 of stream at main chamber outlet Averagegas m/s 648 624 597 210 272 204 consumption at main chamber outletExperimental parametric results A_(oc) × F_(oc) × B_(oc) × C_(oc) ×G_(oc) = 1 ± Δoc A_(oc) — 2.274 2.304 2.259 2.268 2.304 2.246 F_(oc) —0.305 0.0836 B_(oc) — 1.289 1.388 1.077 3.920 3.597 4.100 C_(oc) — 1.2401.173 1.418 1.540 1.750 1.540 G_(oc) — 1.064 1.068 1.074 1.054 1.0681.074 Δoc — 0.179 0.222 0.130 0.229 0.302 0.273 δoc % 17.9 22.2 13.022.9 30.2 27.3

Applicant's teachings also relate to the use of reagents to refinegaseous streams containing pollutants. Refinement of flue gases can becarried out using a multistage vortex counterflow combustion apparatus,which can be similar to the apparatuses 100, 200, 300, 400, 500, 600,700, 800, 900 and 1000. Thermochemical processes in the chamber(s) aretaking place in vortex flows of the mixture of flue gases, water,burning products and/or chemical reagents. Vortex flows can have uniquecharacteristics, can intensify thermochemical processes, and canincrease refinement efficiency. Pollutants targeted during therefinement can include sulfur dioxide SO₂, nitrogen oxides NO_(x) and/orcarbon dioxide CO₂. During refinement, solid and gaseous components canbe produced. Solid components can be non-toxic and can be recycled.Gaseous components, for example, N₂, O₂ and water steam, can be emittedinto the atmosphere without the need for further processing.

Combustion apparatuses taught herein are appropriate for implementationas a thermochemical reactor for at least the following reasons. Hightemperatures promote relatively high chemical reaction speeds, since anincrease in temperature generally leads to an increase in the kineticenergy and number of collisions of chemical particles. Furthermore, thepresence of anisotropic turbulence in a reaction environment can promotemore complete mixing of the reagents, which can also lead to an increasein reaction speed. The presence of intense acoustic oscillations can yetalso lead to the increase of the chemical reaction speed, because it canproduce a mechanical effect on the reagent particles. The reagentparticles are stirred intensively and collide with each other, which canlead to the formation of free radicals on the outer surface of theparticles.

Various chemical reagents can be used, depending on the composition ofthe gaseous stream to be refined and which pollutants are desired to beremoved by the refinement processes. The following examples are intendedto be illustrative but non-limiting.

In a first example, an ammoniac method can be implemented to provide forthe simultaneous refinement of flue gases from SO₂ and NO₂ in thecombustion apparatus. This method is relatively simple and can producefinished products that may be recycled. For the reaction, ammonia NH₃ orcarbamide CO(NH₂)₂ can be used as chemical reagents. Solid products caninclude ammonium sulfate (NH₄)2.SO₄, which is a mineral fertilizer.Gaseous products can include nitrogen N₂ and water steam H₂O. Thefollowing chemical reactions can take place:

4NH₃+3NO₂=3.5N₂+6H₂O−1627.07 kJ/mole  (Eq. 9)

CO(NH₂)₂+H₂O═CO₂+2NH₃+136.08 kJ/mole  (Eq. 10)

It is noted that flue gases can contain nitrogen oxides NO and NO₂, butNO typically immediately oxidizes to NO₂, and therefore only NO₂ isconsidered. Besides the chemical reactions involving the interaction ofNH₃ with NO₂, reactions with sulfur dioxide SO₂ may also be taking placein accordance with the following:

2SO₂+O₂=2SO₃−185.9 kJ/mole  (Eq. 11)

SO₃+H₂O═H₂SO₄−125.2 kJ/mole  (Eq. 12)

2NH₃+H₂SO₄═(NH₄)₂SO₄−275.9 kJ/mole  (Eq. 13)

In a second example, simultaneous use of two chemical reagents can beimplemented for the refining of flue gases from SO₂ and NO₂ in thecombustion apparatus. A first one of the reagents can be NH₃ orCO(NH₂)₂. A second one of the reagents can be powdery sodiumbicarbonate, calcium carbonate, calcium oxide or calcium hydroxide,which can be supplied in atomized form into the combustion apparatus.

In a third example, ammonia NH₃ can be used as the chemical reagent. Thefollowing reaction can take place in the combustion apparatus:

CO₂+2NH₃═CO(NH₂)ONH₄−2,552.73 kJ/kg CO₂  (Eq. 14)

where CO(NH₂)ONH₄ is carbamic acidic ammonium, which can becomecarbamide, is accordance with the following reaction:

CO(NH₂)ONH₄═CO(NH₄)₂+H₂O+483.3 kJ/kg CO(NH₂)₂  (Eq. 15)

A refined product stream from the combustion apparatus can then undergoseparation procedure to separate solid materials from the gaseousstream.

In a fourth example, carbon, water and calcium oxide CaO can be used aschemical reagents. Chemical reactions in the combustion apparatus canproduce calcium carbonate CaCO₃, which can be used as a fertilizer.Calcium carbonate CaCO₃ can also be used for the refinement of fluegases from sulfur dioxide SO₂. The following chemical reactions can takeplace in the combustion apparatus:

CO₂+C=2CO+174.18 kJ/mole or 3,958.64 kJ/kg CO₂  (Eq. 16)

CO+H₂O+CaO═CaCO₃+H₂−199.3 kJ/mole or −1.993 kJ/kg CaCO₃  (Eq. 17)

In a fifth example, CO₂ can be reduced or substantially eliminated froman incoming gaseous stream utilizing the combustion apparatuses asdescribed herein, with which the following sequence of reactions can beperformed:

CO₂+3H₂(Copper and Aluminum Catalyst)→CH₃OH+H₂O  (Eq. 18)

2CH₃OH→C₂H₆O+H₂O  (Eq. 19)

C₄H₈O₂+CH₃OH(H₂SO₄ as a catalyst)→C₃H₆O₂+C₂H₅OH  (Eq. 20)

Equations 18 and 19 can take place in the main chamber, whereas Equation20 can take place in an additional reaction chamber. One or moreseparators and/or chemical storage mechanisms can also be installeddownstream from the additional reaction chamber.

Combustion apparatuses can be tailored for the refinement of variouspollutants from gaseous streams and for the introduction of variousreagents, and are based on vortex counterflow combustion apparatuses,which can complete thermochemical processes required for the refinementof gaseous streams with generally high quality, high speed and highefficiency.

FIGS. 44 to 48 show an apparatus 1100 according to an eleventh exampledescribed in this specification. The apparatus 1100 is similar to theapparatuses 100, 200, 300, 400, 500, 600, 700, 800, 900 and 1000, withlike features identified by like reference numbers. In particular, theapparatus 1100 includes a means for introducing at least one reagent tothe main chamber 1104, as described in further detail below.

Referring particularly to FIG. 46, the first injection zone 1148includes a source of reagents 1186, which can be positioned next to theair or oxidant source 1118. An external source can provide air oroxidant to the source 1118 at an elevated pressure. The source 1186 canintroduce reagents tangentially relative to the direction of fluid flowwithin the first injection zone 1148. Furthermore, tangential supply ofthe reagents via the source 1186 relative to the air or oxidant source1118 can serve to disperse the reagents, which may be in the form of afine powder or particulate. A first pre-chamber 1110 and a fuel source1116 can also be provided as inputs to the first injection zone 1148.The fuel source 1126 of the first pre-chamber 1110 and the fuel source1116 can be connected to, for example but not limited to, a feed ofnatural gas, propane, or diesel fuel.

Referring particularly to FIG. 47, the second injection zone 1172includes a source of reagents 1184, which can be positioned next to theair or oxidant source 1114. The source 1184 can introduce reagentstangentially relative to the direction of fluid flow within the secondinjection zone 1172. An external source can provide air or oxidant tothe source 1114 at an elevated pressure. A second pre-chamber 1108 canalso be provided as an input to the second injection zone 1172. The fuelsource 1122 of the second pre-chamber 1108 can be connected to, forexample but not limited to, a feed of natural gas, propane or dieselfuel.

Referring particularly to FIG. 48, and with continued reference to FIG.45, a third injection zone 1194 produces fluid stream 1178. The thirdinjection zone 1194 is in fluid communication with the at least onethird channel 1176 and delivers the stream 1178 to the afterburnerchamber 1106 proximate to an inlet 1192 of the afterburner chamber 1106.The third injection zone 1194 can be generally annular in shape andextend radially around a circumference of the afterburner chamber 1106.The third injection zone 1194 can include a plurality of swirl vanes1152 for directing rotational fluid flow. The third injection zone 1194includes a source of reagents 1190 and an air or oxidant source 1188.The source 1190 can introduce reagents tangentially relative to thedirection of fluid flow within the third injection zone 1194. Anexternal source can provide air or oxidant to the source 1188 at anelevated pressure.

The thermochemical parameters of temperature, static pressure,ingredients, and the flow structure (temperature fields, pressures andspeeds) can influence the speed of chemical reactions in the apparatus1100, and the refinement of the input stream 1112. Furthermore,concentrations of the chemical reagents and their distribution among thechambers 1102, 1104, 1106 can influence the speed of chemical reactionsin the apparatus 1100. Supply or introduction of the one or morereagents to the chambers 1102, 1104, 1106 can be selectively controlledby the sources 1184, 1186, 1190, respectively. Concentrations ofchemical reagents and their distribution among the chambers 1102, 1104,1106 can be controlled to enable complete or near complete reactions.

Different chemical reagents can be supplied into the apparatus 1100,depending on the components to be refined. Furthermore, the reagentsupplied to source 1184 need not be the same chemical compound as thatsupplied at source 1186, and nor does the reagent supplied to source1186 need not be the same chemical compound supplied at source 1190. Insome examples, it may be desirable to introduce reagents at sources1184, 1186, but not at source 1190. Various configurations are possibleand within the scope of the applicant's teachings herein.

FIGS. 49 to 52 show an apparatus 1200 according to a twelfth exampledescribed in this specification. The apparatus 1200 is similar to theapparatuses 100, 200, 300, 400, 500, 600, 700, 800, 900, 1000 and 1100,with like features identified by like reference numbers. In particular,and similar to the apparatus 1100, the apparatus 1200 includes a meansfor introducing at least one reagent to the main chamber 1204, asdescribed in further detail below.

The apparatus 1200 includes an injection nozzle 1296 for supplying orintroducing a gaseous stream to be refined into the main chamber 1204.In some examples, the gaseous stream can be formed upstream of theinjection nozzle 1296 by the mixture of flue gases along with fueland/or oxidant. The injection nozzle 1296 is positioned at the first end1236 generally at a central apex point of the spherical end surface1282. The apparatus 1200 does not include a primary chamber.

Referring particularly to FIG. 51, the first injection zone 1248includes a source of reagents 1286 and an air or oxidant source 1218. Anexternal source can provide air or oxidant to the source 1218 at anelevated pressure. The source 1286 can introduce reagents tangentiallyrelative to the direction of fluid flow within the first injection zone1248. Referring particularly to FIG. 52, the third injection zone 1294includes a source of reagents 1290 and an air or oxidant source 1288. Anexternal source can provide air or oxidant to the source 1288 at anelevated pressure. The source 1290 can introduce reagents tangentiallyrelative to the direction of fluid flow within the third injection zone1294.

The apparatus 1200 can be implemented in situations where the flow rateof gaseous stream to be refined is relatively high, and also either thetemperature of the gaseous stream to be refined is high enough for thedesired reactions or the reactions can occur at relatively lowtemperature, so heating is not required and thus no primary chamber isnecessary. One limitation to the design of the apparatus 1200 is thatrelatively high stress can be put on the injection nozzle 1296 toprovide the required pressure of gaseous stream being introduced to themain chamber 1204. Another limitation to the design of the apparatus1200 is that there is no second injection zone and thus there is oneless source for supplying reagents.

FIGS. 53 to 56 show an apparatus 1300 according to a thirteenth exampledescribed in this specification. The apparatus 1300 is similar to theapparatuses 100, 200, 300, 400, 500, 600, 700, 800, 900, 1000, 1100 and1200, with like features identified by like reference numbers. Inparticular, and similar to the apparatuses 1100 and 1200, the apparatus1300 includes a means for introducing at least one reagent to the mainchamber 1304, as described in further detail below.

A gaseous stream to be refined is introduced to the first injection zone1348 via inlet or source 1312. An ignition source or igniter 1354 isprovided within the inlet 1312 to ignite the incoming stream as it isbeing tangentially supplied to the first injection zone 1348. Likeapparatus 1200, apparatus 1300 does not include a primary chamber.

Referring particularly to FIG. 55, the first injection zone 1348includes a source of reagents 1386. The source 1386 can introducereagents tangentially relative to the direction of fluid flow within thefirst injection zone 1348. Referring particularly to FIG. 56, the thirdinjection zone 1394 includes a source of reagents 1390 and an air oroxidant source 1388. An external source can provide air or oxidant tothe source 1388 at an elevated pressure. The source 1390 can introducereagents tangentially relative to the direction of fluid flow within thethird injection zone 1394.

The apparatus 1300 can also be implemented in situations where the flowrate of gaseous stream to be refined is relatively high, and also eitherthe temperature of the gaseous stream to be refined is high enough forthe desired reactions or the reactions can occur at relatively lowtemperature, so heating is not required and thus no primary chamber isnecessary.

While the applicant's teachings are described in conjunction withvarious embodiments, it is not intended that the applicant's teachingsbe limited to such embodiments. The applicant's teachings encompassvarious alternatives, modifications, and equivalents, as will beappreciated by those of skill in the art.

1-92. (canceled)
 93. A combustion method comprising: a) generating anaxial vortex stream, and passing the axial vortex stream between a firstend and a second end of a main chamber in a first linear direction; b)generating a peripheral vortex stream, and passing the peripheral vortexstream as a counterflow to the axial vortex stream in a directiongenerally opposing the first linear direction; and c) merging theperipheral vortex stream with the axial vortex stream to form a productstream, the product stream moving in the first linear direction to anoutlet at the second end of the main chamber.
 94. The method of claim93, wherein the axial vortex stream includes a first fuel and theperipheral vortex stream includes a first oxidant, and the first fuel ofthe axial vortex stream and the first oxidant of the peripheral vortexstream at least partially combust to form the product stream.
 95. Themethod of claim 94, wherein the axial and peripheral vortex streams aregenerated having the same rotational polarity.
 96. The method of claim95, wherein, in step (c), the peripheral vortex stream is merged withthe axial vortex stream proximate to the first end of the combustionchamber.
 97. The method of claim 96, wherein, in step (b), theperipheral vortex stream is generated by tangentially introducing afirst stream to the combustion chamber.
 98. The method of claim 97,wherein the first stream is introduced to form the peripheral vortexstream proximate to the second end of the combustion chamber.
 99. Themethod of claim 98, wherein the first stream includes the oxidant. 100.The method of claim 99, wherein the first stream includes a second fuel.101. The method of claim 96, wherein the first stream includes a firstpre-chamber product stream from at least one first pre-chamber, the atleast one first pre-chamber including a source of a second fuel, asource of the oxidant, and an ignition source, wherein the second fueland the oxidant have at least partially combusted in the at least onefirst pre-chamber to form the first pre-chamber product stream.
 102. Themethod of claim 101, wherein the second fuel has a higher heat ofcombustion than the first fuel.
 103. The method of claim 94, wherein theaxial vortex stream is formed upstream from an inlet at the first end ofthe main chamber, and the axial vortex stream is passed through theinlet.
 104. The method of claim 103, wherein, in step (a), the axialvortex stream is generated by passing a second stream, and tangentiallyintroducing a third stream to combine with the second stream.
 105. Themethod of claim 104, wherein the second stream includes the first fueland the third stream includes the oxidant.
 106. The method of claim 105,wherein the third stream includes a second pre-chamber product streamfrom at least one second pre-chamber, the at least one secondpre-chamber including a source of a second fuel, a source of theoxidant, and an ignition source, wherein the second fuel and the oxidanthave at least partially combusted in the at least one second pre-chamberto form the second pre-chamber product stream.
 107. The method of claim106, wherein the second fuel has a higher heat of combustion than thefirst fuel.
 108. The method of claim 93, further comprising cooling theproduct stream to avoid recombination of molecules.
 109. The method ofclaim 108, wherein a fourth gas stream is introduced to the productstream downstream from the outlet to cool the product stream.
 110. Themethod of claim 109, wherein the fourth gas stream is tangentiallyintroduced to the product stream.
 111. The method of claim 94, whereinvelocities of the axial and peripheral vortex streams are controlled toprovide substantially full combustion of the first fuel and the oxidant.112. The method of claim 111, wherein compositions of the axial andperipheral vortex streams are controlled so as to provide astoichiometric excess of oxidant relative to the first and second fuels.113. The method of claim 112, further comprising monitoring combustiondata representing at least one of temperature, fuel quantity, airquantity, and pressure, and using the data as feedback to control theaxial and peripheral vortex streams.
 114. The method of claim 113,wherein the data is gathered using a microprocessor, and themicroprocessor calculates optimum control parameters using amathematical combustion model.
 115. An apparatus comprising a housingincluding interior sidewalls, the sidewalls defining a main chamber, themain chamber including an inlet, an outlet, and first and second ends,the inlet for passing an axial vortex stream to the first end, the axialvortex stream including a first fuel, the second end including an outletfor expelling a product stream, the main chamber including at least onefirst channel disposed between the first and second ends, the at leastone first channel for introducing fluid into the main chamber to form aperipheral vortex stream including an oxidant as a counterflow to theaxial vortex stream.
 116. The apparatus of claim 115, wherein theinterior walls of the main chamber are generally cylindrical andconverge in a flow direction of the axial vortex stream from the firstend to the second end.
 117. The apparatus of claim 116, furthercomprising a merging surface within the main chamber for merging theperipheral and axial vortex streams.
 118. The apparatus of claim 117,wherein the merging surface is located along the sidewalls of the mainchamber at the first end thereof.
 119. The apparatus of claim 118,wherein the merging surface is frusto-toroidal in shape.
 120. Theapparatus of claim 115, wherein the inlet comprises a cylindrical sleeveextending into the main chamber, the sleeve for directing flow of theaxial vortex stream into the main chamber.
 121. The apparatus of claim120, wherein the sleeve is frusto-conical in shape.
 122. The apparatusof claim 121, wherein the sleeve includes a plurality of apertures. 123.The apparatus of claim 115, further comprising a first injection zonefor producing a first stream, the first injection zone in fluidcommunication with the at least one first channel for providing thefirst stream to the main chamber, the first stream forming theperipheral vortex stream.
 124. The apparatus of claim 123, wherein thefirst injection zone is generally annular in shape and extends radiallyaround a circumference of the main chamber.
 125. The apparatus of claim124, wherein the first injection zone includes a plurality of swirlvanes for directing rotational fluid flow.
 126. The apparatus of claim123, wherein the first injection zone includes an oxidant source forinjecting an oxidant to form at least a portion of the first stream.127. The apparatus of claim 126, wherein the oxidant source istangentially aligned within the first injection zone.
 128. The apparatusof claim 123, wherein the first injection zone includes a fuel sourcefor injecting a second fuel to form at least a portion of the firststream.
 129. The apparatus of claim 128, wherein the fuel source istangentially aligned within the first injection zone.
 130. The apparatusof claim 123, wherein the first injection zone includes at least onepre-chamber, the at least one pre-chamber including a fuel source forsupplying a second fuel, an oxidant source for supplying an oxidant, anigniter, and an outlet for exhausting a second pre-chamber productstream.
 131. The apparatus of claim 130, wherein the outlet of the atleast one pre-chamber is tangentially aligned within the first injectionzone.
 132. The apparatus of claim 115, further comprising a primarychamber in fluid communication with the inlet of the main chamber, theprimary chamber including a primary inlet for receiving a second stream,and at least one second channel for supplying a third stream, the secondand third streams mixing in the primary chamber to form the axial vortexstream.
 133. The apparatus of claim 132, wherein the primary inlet isconnected to a source of the first fuel, the first fuel forming at leasta portion of the second stream.
 134. The apparatus of claim 133, furthercomprising a second injection zone for producing the third stream, thesecond injection zone in communication with the at least one secondchannel for providing the third stream to the primary chamber.
 135. Theapparatus of claim 134, wherein the second injection zone is generallyannular in shape and extends radially around a circumference of theprimary chamber.
 136. The apparatus of claim 135, wherein the secondinjection zone includes a plurality of swirl vanes for directingrotational fluid flow.
 137. The apparatus of claim 134, wherein thesecond injection zone includes an oxidant source for injecting anoxidant to form at least a portion of the third stream.
 138. Theapparatus of claim 137, wherein the oxidant source is tangentiallyaligned within the second injection zone.
 139. The apparatus of claim134, wherein the second injection zone includes at least onepre-chamber, the at least one pre-chamber including a fuel source forsupplying a second fuel, an oxidant source for supplying an oxidant, anigniter, and a pre-chamber outlet for exhausting a second pre-chamberproduct stream.
 140. The apparatus of claim 139, wherein the pre-chamberoutlet of the at least one second pre-chamber is tangentially alignedwithin the second injection zone.
 141. The apparatus of claim 115,further comprising an afterburner chamber in fluid communication withthe outlet of the main chamber, the afterburner chamber for receivingthe product stream and cooling the product stream.
 142. The apparatus ofclaim 141, wherein the afterburner chamber includes at least one thirdchannel for introducing a fourth stream to the product stream, thefourth stream comprising a coolant fluid.
 143. The apparatus of claim142, further comprising a third injection zone for producing the fourthstream, the third injection zone in fluid communication with the atleast one third channel for providing the fourth stream to theafterburner chamber.
 144. The apparatus of claim 143, wherein the thirdinjection zone is generally annular in shape and extends radially arounda circumference of the afterburner chamber.
 145. The apparatus of claim144, wherein the third injection zone includes a plurality of swirlvanes for directing rotational fluid flow.
 146. A method of gasrefinement, comprising: d) providing an axial stream, and passing theaxial stream in a main chamber in a first linear direction from a firstend towards a second end, the axial stream including at least onepollutant; e) generating a first peripheral vortex stream, theperipheral vortex stream including at least one reagent; and f) mergingthe first peripheral vortex stream with the axial stream to form aproduct stream, the at least one pollutant and the at least one reagentat least partially reacting in the product stream, the product streammoving in the first linear direction to an outlet at the second end ofthe main chamber.
 147. The method of claim 146, wherein the at least onepollutant is selected from the group consisting of SO₂, NO_(x) and CO₂.148. The method of claim 147, wherein the at least one first reagent isselected from the group consisting of NH₃, CO(NH₂)₂, C, H₂O and CaO.149. The method of claim 146, wherein the at least one pollutant isselected from the group consisting of SO₂ and NO₂, and the at least onereagent is selected from the group consisting of NH₃ and CO(NH₂)₂. 150.The method of claim 149, wherein the peripheral vortex stream furthercomprises at least one second reagent selected from the group consistingof NaHCO₃, CaCO₃, CaO and Ca(OH)₂.
 151. The method of claim 146, whereinthe at least one pollutant comprises CO₂, and the at least one reagentis selected from the group consisting of NH₃, C, H₂O and CaO.
 152. Themethod of claim 146, wherein, prior to step (c), the peripheral vortexstream is passed as a counterflow to the axial vortex stream in adirection generally opposing the first linear direction.
 153. The methodof claim 152 wherein, in step (c), the peripheral vortex stream ismerged with the axial vortex stream proximate to the first end of themain chamber.
 154. The method of claim 146, wherein, in step (b), theperipheral vortex stream is generated by tangentially introducing afirst stream to the combustion chamber, the first stream including theat least one first reagent.
 155. The method of claim 154, wherein, instep (b), the first stream is tangentially introduced proximate to asource of the at least one first reagent.
 156. The method of claim 155,wherein the first stream comprises an oxidant.
 157. The method of claim156, further comprising introducing a fuel to the first stream.
 158. Themethod of claim 146, wherein, in step (b), the first peripheral vortexstream is generated at least in part by tangentially introducing a firstpre-chamber product stream from at least one first pre-chamber, the atleast one first pre-chamber including a source of a fuel, a source ofthe oxidant, and an ignition source, the fuel and the oxidant at leastpartially combusting in the at least one first pre-chamber to form thefirst pre-chamber product stream.
 159. The method of claim 146, furthercomprising cooling the product stream to avoid recombination ofmolecules.
 160. An apparatus for gas refinement, comprising: g) ahousing including interior sidewalls, the sidewalls defining a mainchamber, the main chamber including first and second ends and an inletfor introducing an axial stream that passes in a first linear directionfrom the first end to the second end of the main chamber, the axialstream including at least one pollutant, the second end including anoutlet for expelling a product stream; h) at least one first channeldisposed between the first and second ends of the main chamber; and i) afirst injection zone for producing a first stream, the first injectionzone including a source of at least one first reagent, the firstinjection zone in fluid communication with the at least one firstchannel for providing the first stream to the main chamber to form aperipheral vortex stream, the at least one pollutant in the axial streamand the at least one reagent in the peripheral vortex stream at leastpartially reacting in the product stream.
 161. The apparatus of claim160, wherein the at least one pollutant is selected from the groupconsisting of SO₂ and NO₂, and the at least one reagent is selected fromthe group consisting of NH₃ and CO(NH₂)₂.
 162. The apparatus of claim160, wherein the at least one pollutant is CO₂, and the at least onereagent is selected from the group consisting of NH₃, C, H₂O and CaO.163. The apparatus of claim 160, wherein the first injection zone isgenerally annular in shape and extends radially around a circumferenceof the main chamber.
 164. The apparatus of claim 163, wherein the firstinjection zone includes a plurality of swirl vanes for directingrotational fluid flow.
 165. The apparatus of claim 164, wherein thefirst injection zone includes an oxidant source for injecting an oxidantto form at least a portion of the first stream.
 166. The apparatus ofclaim 165, wherein the oxidant source is tangentially aligned within thefirst injection zone.
 167. The apparatus of claim 166, wherein theoxidant source is proximate to the source of the at least one firstreagent.
 168. The apparatus of claim 160, wherein the first injectionzone includes a fuel source for injecting a fuel to form at least aportion of the first stream.
 169. The apparatus of claim 160, whereinthe first injection zone includes at least one pre-chamber, the at leastone pre-chamber including a fuel source for supplying a second fuel, anoxidant source for supplying an oxidant, an igniter, and an outlet forexhausting a second pre-chamber product stream.
 170. The apparatus ofclaim 160, further comprising an afterburner chamber in fluidcommunication with the outlet of the main chamber, the afterburnerchamber for receiving the product stream and cooling the product stream.